Test device for flight controls



June 15, 1965 w. MLLER TEsT DEVICE FOR FLIGHT coNTRoLs Filed Nov. 18, 1959 4 Sheets-Sheet 1 ,"IANVENTOR wALoEMAR MLLER June irs, 1965 Filed NOV. 18, 1959 4 Sheets-Sheet 2 wALDEMAR MLLER i June 15, 1965 w. MLLER 3,188,852

TEST DEVICE FOR FLIGHT CONTROLS Filed Nov. 18, 1959 4 Sheets-Sheet 3 y Fg INVENIQR. WALDEMAR MOLLER June 15, 1965 w. MLLER l 32,188,852

TEST DEVICE FOR FLIGHT' CONTROLS A Filed Nov. 18, 1959 4 sheets-sheet `4 60 ISO INVENTQR. WALDEMAR MOLLER BY 4f/f lf j ight' controls.

United States Patent O 3,133,852 TEST DEVHCE FLEGHT CNRQLS Waldemar Mller, berlingen (Bodensee), Germany, as-

signer to Bodenseewerlr Perkin-Eimer da Co., @.mbdt., berlingen ('iodensee), Germany Filied Nov. 13, 1959, Ser. No. 853,797 l) Claims. (Cl. 7S-l) `This invention relates to a device for testing automatic More specifically, the device of this invention permits the behavior of airborne objects under the influence of a control instrument to be thoroughly tested without the necessity of carrying out flight tests. Furthermore, the invention permits the characteristics and parameters influencing the behavior of the airborne object to be varied within required limits.

According to the invention, there is provided a rotatable turn table which accommodates the control equipment under test. The turn table is driven-through a drive gear-by a controllable electric motor, controlled by adjustable dynamic control parameters. The control parameters are derived from the control surface deiiection and from the angular velocity of the turn table. Those parameters correspond to the skidding angle and y the characteristics of the airborne object, so that the turn table rotation is a representation of the movement of the 'airborne objects center of gravity.

With such a dynamic test bench, it is possible to observe in the laboratory, in the course of a few minutes, the dynamic behavior of the aircraft or airborne object under the influence of the iiight controls over a wide range of speeds or dynamic pressures, and with any posinstability begins and the application of Hight control would endanger the aircraft.

The invention is equally important in the mass production of iiight controls, for the purpose of adjustment and final functional control of each individual instrument. It is additionally useful in current service control, in order to determine time changes of the control characteristics as a result of the wear of individual control elements and thereby exclude possible dangers to the aircraft. With flight control instruments (for instance those for unmanned airborne objects) which have been stocked for a longer period of time, the dynamic test bench per- /mits a rapid determination as to Whether or not they are still in perfect operating condition. On an airport or in a missile launching center, the serviceability of flight control instruments can be checked by means of the dynamic test bench before they are put into operation.

An embodiment of the present invention, with several advantageous design features, is given hereafter. The attached drawings represent:

FIG. l, block diagram of a test device according to the invention.

FiG. 2, schematic representation of the means for testing and Calibrating the test device.

FIG. 3, schematic representation of the means for electric detection of the turn table oscillations.

FIGS. 4 and 5, mechanical design of the test devices.

The dynamic test bench is provided with a control surface tap RL which is connected to the control surface, controlled by the servo motor RM of the flight con- 3,188,852 Patented June l5, 1965 trol, and delivers an electric signal proportional to the control surface deflection.

The bench is further provided with a turn table P1 which can be rotated by means of a two-phase electric motor (Ferraris motor) M through a reduction gearing M2. The control instrument St of an autopilot can be fitted to the turn table, its output amplified, if desired, by amplifier STA, and supplied to servomotor RM.

The angular position of the dynamic test bench turn table represents the position angle of the aircraft, for instance the azimuth angle 1/1. K

A deflection of the control surface tap RL from its zero position is represented by a corresponding rotation of the turn table Pl of the dynamic test bench. The relation-both with regard to magnitude and timeexisting between the angular position of the turn table and the deflection of RL is subject to the same laws as the relation existing between the position angle of the aircraft and the control surface deflection.

The rotary movements of the aircraft-more accurately: the angular accelerations-are determined by the magnitude of the applied torques and by the moment of inertia I of the aircraft about the axis concerned. On the dynamic test bench, we have the moment of inertia I' of the turn table and the building elements coupled to it: (motor, gearing, control instrument), this is smaller by the factor f (perhaps of the order of magnitude of 106) than the moment of inertia of the aircraft. The turn table will therefore carry out the same rotations as the aircraft, provided the torque generated by the motor is the reproduction-reduced at the ratio of 1:fof the torques acting on the aircraft.

As an example, we may consider the case of the heading control, i.e. the case of the rotation of the aircraft about the yaw axis. These rotations are mainly generated by the following torques:

(a) The moment generated by the rudder deflection g. it can be considered as approximately proportional `t0 i'.

(b) The moment of directional stability. It is proportional to the skidding angle (c) The moment of turn damping. to the angular velocity lwzzr/f.

(d) In addition, there are interfering moments of various origins, for instance due to gusts etc.

The total yawing moment on the aircraft has accordingly the following formula:

It is proportional N nowZ-nsmB-nRg (-1- interfering moments) (with the normal determination of signs no, ngt and nR are generally positive). The angular acceleration resulting from this is:

il= ]I-V= -aDwz ast aRi -linterfering moments) :adp-ast-CLRH-linterfering moments) The coefficients n0, ngt, :VIR or aD, ast, aR depend on the aircraft design and on the flying speed and the air density.

On the test bench, the torque generated by the Ferraris motor M, and consequently also the angular acceleration of the turn table Pl is proportional to the product of the exciter voltage UEM. and the control voltage Us, of the motor:

lbzcUErrUst The exciter voltage is adjustedby means of a rotary knobto a value proportional to aR:

UErrECaR (3)(-1- interfering moments) If this condition is met and if the coefficients c and c" have been selected appropriately (namely ccc=-1),

the same equation as for the aircraft will apply for the dynamictest bench:

gli: -aDtl/i-astf dR (-j-interfering moment) l ,'The control voltage for themotor M Vis supplied by an Y amplifier HV int-o which the following input voltages are fed:

(a) A signal proportional to the control surface deflection g, supplied by the control surface tap RL,

(b) VA signal proportionalto the speed of rotation of the turn table, supplied'by a tachometer generator G coupled to the motor M, p

(c) A signal proportional to the skidding angle ysupplied by the tap SW,as willbe explained later in this application,

(d) Aninterference signal, if required, fed into the test bench from outside. y Y

i The signal proportional to the skidding angle is obtained as follows.

the plane of symmetry of the aircraft and the trajectory be adjusted to 10x or 100x., the standard value.

. Y 4 not to place excessively large and heavy instruments on the turn table P1, as the moment of inertia of the control instruments is added to that of the turn table, thus reducing the possible values of angular acceleration. In general, tests should be carried out at a rdefinite standard value of the moment of inertia I." If themoment of iner- 1 tia-with mounted control instrumentsis below this value, it is set to the standard value by the addition of correcting discs in the shaft `of the motor M. In addition,

there are discs S which allow the moment of inertia I to Smaller values of aR can then be more easily set.

Instead of the Ferraris motor M, described in this embodiment ofthe invention, another controllableasynchronous/motorY can also'be used. As the driven turn table P1 is to simulate the movements of the yairborne object,

- it is `necessary to keep friction very low'and to provide a the control of the motor- M canserve for the representa- The skiddingv angle is the angle between I tangent. The position of the plane of'symmetry is represented on the dynamic test bench by the position of the turn table. The test bench must therefore include a com ponent which represents the direction of the trajectory tangent. VIt is then possible to represent the required signal is used, which results from the equilibrium Ybetween the skidding lateral force and the centrifugal force. v

As may be seen from FIG. 1, the signal produced by the tap SW, which is proportional to is amplifierby tap namplifier SWA and fed into an integrating motorv M whose speed is proportional to this signal. A reduction gearing M2 connected to this motor supplies at its;driv axis the direction of the trajectory tangent. This axis carries the stator SWS ofthe tapSW, whereas its rotor SWR is fixed to the axis of the turn table P1.

In the same manner as described for Vthe heading control, "the pitch control may be tested by means of the dynamic test bench. In the case of'band control, the signal is not used. f Y Y 1 (a and ast=) In order to test a given aircraft under a given flight condition, one must know the four parameters (for each axis) aR, dD, ast and a' aR must be considered the most important as it characterizes the aircraft insofar as flight control is concerned. It has the `physical meaning:

Angular acceleration divided by Vcontrol surface deflection, and the dimension see-2.

With a well designed flight control, the remaining para-` meters aD, ast, a, are often of less importance. In most cases, it is possible to obtain a relatively correct picture Aof thebehavior of the aircraft Ywith the flight control, by assuming a-Op A roughapproximation may even be possible by assuming abv=ast=a=0. Asralready stated, adjustment ofthe parameter 1R on the testbench is ef# fected bymeans of the exciter voltage of the motor` M.

The upper limit of the adjustable aR' values is deter-l mined bythe characteristics of the test bench, in particular' i by the characteristics ofthe drive motor M. It is advisable tion of gusts. It can, for example, be taken from a computer which determines theinfluence exercised, for instance, Vduring the test of a control instrument by aircraft inclination about the pitch or roll axes. `It is possible Ato couple together, through'the intermediary of such a computer if required,A several test kdevices of the type described, so that control instruments can be tested simultaneously Vfor the three axes of the airborneobject,^taliing into consideration the. inuence they exercise on each other. v j f Y The device shownin FIGURE 2 will carry out in a convenientV way the currentcontrol'and adjustment of the parameters of the equationof'moments, takinginto consideration the necessary amplifiers."

' f In accordanceV with theinvention, this problem is es-v ,'sentially solved by incorporating -a chr-onornetric system for the calibration and adjustment of the test device; The chronometer cany be disconnected automatically by a switching device controlled bythe movements ofthe turn table. y a check of eachk parameter can beobtained by a time measurement of the turn table'motion.

It is'advisableto connect the chronometric system by 'means of a control switch which connects a particular control parameter-to the test device. -For `calibration and adjustment ofthe test device, it is necessary, among otheritems, '..to corre1ate a definite rotary acceleration of the turn table with a definite input signal. The rotary acceleration e of the turn table can'be derived from the time t, which the turn table requires for a definite iangular distanceY Y surface potentiometer is connected to the testdevice at .aadeiinite control surfacejposition, it is possible to measure the Vrotary acceleration ofthe turn table .at that position .and to compare it with the provided rated value, so that adjustment o f thecontrol Surface efliciency is possible.

' VIf the rotary acceleration corresponding to a definite signal of the control surfacezpotentiometer is not reached or exceeded,'this shows that the mechanical link between the contr-o1v surface potentiometer and the control surface The inventionis based on the knowledge that yrotated by an integrating motor M.

kit at the twentieth pulse. the voltage tapped at the tapping system SW passes through zero, so that ten full oscillations are counted.

snsaeea of the airborne object does not correspond to the specified transmission ratio and must be changed.

1 Simultaneously with a particular control signal, a damping signal may be connected to the test device which is generated yby a tachometer generator G coupled with the turn table drive motor M. A turn table rotational speed Will then be obtained which can be determined without diicul-ty .by means of the chronometric system `and compared with the rated value. Thus, it is possible to examkine and adjust the damping signal.

Another embodiment of the invention provides for c-onnection and disconnection of the chronometric system by means of a counter which counts a definite number of oscillations of the turn table. As described `above in n more detail, -a stabilizing signal proportional to the skiddi-ng angle is supplied by the tap SW, whose Vrotor SWR is connected to .the turn table and Whose stator SWS is The dynamic ciiect of this stabilizing signal can be checked and set in the following way. If, at zero position of the turn table, a definite signal from the tap is connected to the test device,

the turn table-after disconnection of the integrating motor M .and after being'pushed-Awill oscillate about the rzero position with a definite frequency. The frequency depends on the magnitude of the signal supplied by the tap SW and on the excitation of the turn table drive -moton By means of the chronometric system, in conjunction with the counter counting the turn table oscillations, itis possible to determine the oscillation frequency of the turn table Vand to compare it with a rated frequency corresponding to `a denite signal level. In practice, the arrangement is made in such away that lthe chro-nometric vsystem is connectedy by the counter at the first oscillation 'and disconnected at the tenth oscillation.

In the above way, it is possi-ble to examine and set, by

ymeans of the chronometric system and by means of appropriate switching measures, all parameters of the equa- `its contact `It-a synchronous clock SU, `and simultaneously-through its contact 2-a control signal to the main amplifier HV of the test device. As stated above, a lovv inertia motor M for the drive of the turn table P1 is connected to the main amplifier HV. The motor M is coupled to a tachometer generator G. The rot-or of tapping system SW is rotated together with turn table Pl. The stator is rotated-by means of a gearing MZ-Aby an integra-ting motor M. The integrating motor M is connected by means of Ia switch S, to .an amplier V5, whose input is connectedthrough an adj-usting means 1V-to the tapping system SW. The tapping system SW is further connected-through an adjusting means ast/QR to the input of the main amplilier HV, whose gain can be adjusted by means of the adjustment device BHV. By

Lmeans of the switch S, a Contact type counter ZW can be connected upon disconnection of the inte-grating motor ML-to the amplifier Vp.

The counter ZW serves for connection and disconnection of the synchronous clock SU. It is so arranged that it connects the clock SU at the first pulse and disconnects A pulse is emitted each time For checking and adjusting the main amplifier HV, the control switch KS is operated yand thus the synchronous clock SU is connected and simultaneously a control signal is passed through contact 2 to the main amplifier HV, under whose influence the turn table Pi is accelerated.

After a deiinite angular movement of 90, 180 or 270, the switching device SV is operated by a cam N on control disc SSwhich in turn energizes the release relay RA, which disconnects the synchronous clock SU. From the time indicated by the synchronous clock, the angular acceleration of the turn table P1 can .be deduced as stated above, .and compared with a rated value corresponding to the control signal. By adjustment of the gain on the adjustment device BHV, coincidence with the rated value can 4be obtained.

instead of the control signal, a signal from a control surface potentiometer can be connected to the main ampiier HV through Contact 2, and the angular acceleration of the turn table Pil can be determined in the same way. Coincidence with the rated value can then be obtained by adjustment of the control surface potentiometer. if, simultaneously with the control signal, a damping signal taken from the tachometer generator G is connected to the ampliiier, the angular speed of the turn table i'll is a measurement of the eficiency of the damping signal. This angular speed can easily be determined from the chronometric value indicated by the synchronous clock SU after a full rotation of the turn table Pi.

For adjustment and checking of the stabilizing signal, the switches S and 3 are thrown in such a way at the zero position oi the turn table Pi that the integrating motor M is disconnected from the amplifier V, and the counter ZW connected. If the turn table is pushed-with disconnected damping-it will oscillate about its zero position, with a frequency dependent on the setting of the adjustment means ast/(1R. As soon as the voltage taken from the tapping system SW passes through zero during the first oscillation, the counter ZW obtains the first pulse and connects the clock SU. After the tenth osciilation of the turn table Pit, the synchronous clock SU is disconnected,

so that it indicates the time consumed for ten full oscillations. The frequency of the turn table oscillation can then be calculated as a measure of the stabilizing signal taken from the tap. Coincidence with the rated value can be obtained by operation of the adjustment means ast/(ZR.

With the described test device, the movements to be executed by the airborne object about the center of gravity under the influence of both external interference moments and reaction of the control instruments, are represented as turn table movements. Frequently these are transient osciliations whose amplitudes depend on the magnitude of the connected interference moments and the reaction of the control instrument to be tested. It is very advantageous if these transient oscillations can be recorded with maximum sensitivity and accuracy or shown on an oscilloscope. For this purpose, a recording potentiometer or similar device can be provided having a cam rider controlled in accordance with the angular deflections of the turn table. if the rider is dimensioned in accordance with the maximum oscillation amplitudes of the turn table, amounting for instance to i3 recording will become insensitive and inaccurate at small oscillation arnplitudes (for instance i5).

The object of the device according to FIG. 3 is to allow recording of the turn table oscillations with suflicient sensitivity in spite of varying amplitudes. According to the invention, this is obtained by the fact that the turn table is connected to a control disc provided with several cams, displaced with regard to each other, and covering different angular ranges for the control of a rider. For the control of the recorded potentiometer cam rider, one of these cams whose slope is adapted to the expected osciilation amplitudes, can be selected. The cam with the maximum slope, i.e. the one which covers only a small angular range, will be used with small oscillation amplitudes. For larger oscillation amplitudes, the cams with correspondingly iiatter slope can be used. By this system, the recording potentiometer will be fully controlled by one for each angular range, with the turn table fother.

Arepresented in schmatic FIG.' 1.

and its'attached control disc being displaced'in` sucha way Athat in each case, the center of the-cam to be used de-` t Yterminesthe zero point. Y i i s In another embodiment-of the invention, the recording potentiometerrider applied to ther camrby'meansofa control element, is spring loaded and seated onfan adv justed'leversupporting the recording. potentiometer. For the purposeV of protecting the potentiometer and the cams,

the lever can-be adjusted away4 from the control disc and the rider put out of operation if it is not required for further tests. s Y l v, i

vA control disc SS is connected .-to the turntable P1.

The turn table P1 is drivenas stated aboveby a low inertia electric motor which is coupled to a-tachometerV generator G.y The electric motor is fed from a main amplifier HV, which among other items-is controlled by an interference magnitude marked by an arrow SG. s

The control disc SS is provided with four cams Hl-Hrl, whose centers are displaced lby 90 with regard to each The cam H1 covers an angular range of i5", it

has accordingly a relatively steep slope. The cams H2,

H3 and Hpcover larger angular ranges'of `1:10, Vand 120,

and i30.

On a lever 5, pivoted at 1, a riderv 6 is orientably positioned'at 7 and supported by a spring 8. A control pin turn table P1.V The rider 6 taps a measuring voltage from a bridge connected recording` potentiometer 10. The

recording potentiometer 10. .is located on the lever 5.- Y The tapped measuring voltage is fed into a recorder-such as an oscilloscope 11. Y t

` If the turn table P1 makesl a transient oscillation under the influencerof the interference moment SG andthe re-V action of the control instrument to` be tested, the rider A is accordingly controlled through `the intermediary .of l

.the control pin vand the cam H1, and taps a measuring voltage from the recorderV potentiometer 10, representing the oscillation of'theyturn table P1 whose curve is recorded on the instrument Y11. It for this purpose, the

steep slope cam Hlis used, the recorder-potentiometer Q10V is fullygcontrolled overV its entire range with turn table ,oscillationamplitudes of i5". If the; turn table P1 is rotated to aV zero position, where the cam H2 is in contact the control pin 9, a full potentiometer rangecontrol is l obtained withl oscillation amplitudes lof 110. WhenY using the cams H3 and H4, ,full potentiometer range con-V trol is obtained at i20 and 1h30", respectively.

If no. recordings are made, the recorder unitY 11 is disconnected and lever` 5 oriented away from the control disc SS. The turn table P1 can then move freely for other tests without friction from the control pin 9.

V9 is connected to therider 6 and applied to one of the -cams H1 to H4, according toswhich one of the came H1 to H4 has been put into operation by displacement of the .40 with the turn table P1 and the` drive and vadjustment vmeans lcan be placed on the positioning pins `20.v On its bottom and on one lateral face, the vinstrument top housing is provided with positioningsockets 50 and-60 to t into the positioning pins.v 20. It is therefore possible to Iplace the,r positioning sockets 5,0 of the-topfhousing 40 on the positioning pins 20,`(FIG.-l); to provide for a horizontalarrangement of the 'turn tablePl. I-t is also pos.-

' sible tointr-oduce the positioning pins 20 into the position-l ing sockets 60 (FIG. 2), sothat thetop housing is tilted Yby 90 and the turn table Yaccordingly provided 'in a vertical position. lThe electrical connections of the top housing .40 areconne'cted to two multiple plugs 70,r 70', which are Aso arranged that in each `case one of them (either 70 or 70') is introduced into socket 30 of the base compartment when placing the top housing on it. v

Iclaimq, y r i f 1f.j Apparatus rfor the ytesting of Yautopilots which comprises turntable means adapted to support a unit under test; variable speed electric'motor means having a manual- Y 1y variableeld adjustment means'which can-be set in accordance withthe characteristics of an objecty ordinarily controlled by the autopilot, said motor.y meansbeing v in drivingvrelationshipito said turntable means; iirst signal `generatingmeans having Aa first output proportional to a simulated skidding angle; second'signal generating meansy having a second output proportional to control surface deectiom third signalV` generating means havingV a third output proportional to the rotational velocityy of said turntable means; and control means responsive/to said 'iirstp second, and third outputs vto control `said variable Vspeed electric motor means.

2. The'appar'atus of'claim 1 Whereinsaid motor means lcomprises a twoY phase Vmotor having a irst winding energized inaccordance with the characteristics of a controlled yobjectand a second winding energized by said control means;

Y 3. The apparatus 'y of claim V1l wherein said tirst signal Y generatinglrmeans comprises? avoltage pickoif having fa trstrotatable element positionable in accordance with the direction of the tangent to a simulated night path, a second rotatable element positionable in accordance vwith the heading fof a simulated controlled object, and means for `producingan youtput signal proportional to the yangular When testing flight control instruments, in particular Athose required for pitch androll control of the aircraft,

gravity influences must be considered which are excluded with a horizontal arrangement of the turn table, such as carry out such tests in a simple way, the test deviceof the `invention is so arranged that the-turn table and its drive system are accommodated in a separate housing which' can be positioned either horizontally or vertically on a rack-type base compartmentcontaining the amplierrunit.' For this purpose, the base compartment is provided with four positioning pins on thetop face,.while the bottom and one lateral face of the top housing are each provided with four matching positioning sockets. l

The connections of the top housing are connected to two :multiple plugs. When placing the top housing on the base,

one of these is introduced into a matching socket Yin the ,base compartment, In this way, it is'possible to use the test device both with the horizontally 'and the vertically Hpositioned turn table, without having to undertake timeconsuming operations for the establishment ofY the necessary conections. l

In order toY be able to` ditference; between said tangent kand said heading.

4. The apparatus of claim 2 wherein said motor means Vincludes means for adjusting the moment of inertia 'of said motor vmeans and said turntable means.

5; The apparatusy of claim 1 kwherein said turntable means includes means forselectively positioning: said VKturntable for rotation about oneof a vertical and horizontal axis.

6. Apparatus for the testing of autopilots 'which cornprises turntable meansV adaptedto support a unit under test; variable speed electric motor means,y in driving relationshipY to said turntable meansg'rst signal generating means havinga tirst output proportional to a simulated skidding angle; second signalgenerating means havingk a secondoutput proportionalV to'control surface deiiection;

third signal generating means having a'third output proportional to the Yrotational velocity of said turntable means; controlV means responsive to said rst, second, and

third output to control said variable Yspeed electric motor means; timingmeans operable during the rotation' of said/turntablek means; and actuatingmeans adapted to actuate said timing means during a predetermined movement of said turntable.

7. The apparatus of claim 6 wherein said actuating 10. The apparatus of claim 8 wherein said actuating means includes means for applying a control parameter means includes cam means rotatable with said turntable signal to said control means. 11163115- 8. The apparatus of claim 6 wherein said actuating References Cited by the Examiner means actuates said timing means during a predetermined 5 UNITED STATES PATENTS angle of rotation of said turntable means.

9. The apparatus of claim 6 wherein said actuating JOOJSSS 1/55 Good et 73"1 means actuates said timing means during a preselected 704644 3/55 Good et a' number of oscillations of said turntable means. lo ISAAC LISANN, Primary Examinen 

1. APPARATUS FOR THE TESTING OF AUTOPILOTS WHICH COMPRISES TURNABLE MEANS ADAPTED TO SUPPORT A UNIT UNDER TEST; VARIABLE SPEED ELECTRIC MOTOR MEANS HAVING A MANUALLY VARIABLE FIELD ADJUSTMENT MEANS WHICH CAN BE SET IN ACCORDANCE WITH THE CHARACTERISTICS OF AN OBJECT ORDINARLY CONTROLLED BY THE AUTOPILOT, SAID MOTOR MEANS BEING IN DRIVING RELATIONSHIP TO SAID TURNABLE MEANS; FIRST SIGNAL GENERATING MEANS HAVING A FIRST OUTPUT PROPORTIONAL TO A SIMULATED SKIDDING ANGLE; SECOND SIGNAL GENERATING MEANS HAVING A SECOND OUTPUT PROPORTIONAL TO CONTROL SURFACE DEFLECTION; THIRD SIGNAL GENERATING MEANS HAVING A THIRD OUTPUT PROPORTIONAL TO THE ROTATIONAL VELOCITY OF SAID TURNTABLE MEANS; AND CONTROL MEANS RESPONSIVE TO SAID FIRST, SECOND, AND THIRD OUTPUTS TO CONTROL SAID VARIABLE SPEED ELECTRIC MOTOR MEANS. 